Abstract: The invention relates to a method and system for supporting pilots in landing helicopters in visual flight under brownout or whiteout conditions. According to the invention, 3D data of the planned landing site are generated during the approach for landing, and are accumulated into a 3D representation of the landing site with the aid of position and attitude data of the helicopter. From this 3D representation, a virtual external view is continuously generated corresponding to the perspective of the actual position and attitude of the helicopter and is displayed for the pilot. A control routine ensures that no 3D data of the planned landing site that are generated under brownout or whiteout conditions are taken into account in the accumulation of the 3D representation.

Abstract: An aircraft flight control display for orientation of the pilot during an approach of the aircraft toward a destination has a center of the display as its fixed point. An aircraft symbol with a center depicts the longitudinal axis as well as a lateral line to depict the current attitude of the aircraft. A destination position symbol has a reference line and a position symbol, with a skyline having a center. The destination position symbol is located at a distance from the center and its reference line points to the center as the reference point. The destination position symbol is rotated around the reference point dependent on the relative position of the aircraft's direction or the flight direction to the desired destination direction.

Abstract: A linear frequency-modulated pulse radar system is provided in which the echo signal is mixed with a de-ramp signal, in order to reduce the bandwidth. The transmission signal of the pulse radar and the de-ramp signal are generated with the same reference oscillator, whereby the transmission signal and the de-ramp signal are generated as the upper and lower side band of an upward mixing process.

Abstract: A system for protecting a vehicle against IR-guided missiles, includes at least one missile warning device, and a device for jamming IR-guided missiles. A laser array is coupled to the at least one missile warning devices for jamming the IR-guided missiles.

Abstract: Apparatus and method for handling workpieces using a suction gripper having a suction plate including a plurality of suction openings connected to a vacuum source. The apparatus includes at least one vacuum source, a suction plate having a plurality of openings, at least one movable template, which defines an active area, positionable on the suction plate, and at least one pair of fans arranged to be contrarotating.

Abstract: An arrangement for a junction between a microstripline and a waveguide is provided. The arrangement includes a microstripline fitted on the upper face of a dielectric substrate, a waveguide fitted on the upper face of the substrate and has an opening on at least one end surface and has a structure which is in the form of a step or steps in the area of the opening on one side wall and is conductively connected in at least one part to a microstripline. One side wall of the waveguide is a metallized layer formed on the substrate. A cutout is formed in the metallized layer and into which the microstripline projects. A rear-face metallization is formed on the rear face of the substrate, and electrically conductive via holes between the metallized layer on the upper face of the substrate and the rear-face metallization, which surround the cutout.

Abstract: A method for the detection and combating of forest and surface fires includes the steps of observing and detecting fires using an infrared camera on board an observation aircraft; georeferencing image obtained by the infrared camera pixel-wise using location data of the observation aircraft as obtained by a satellite navigation system; testing the georeferenced infrared image for hot points caused by a fire, and transmitting coordinates of the hot points via a data link to a central data processing system on the ground; automatically generating deployment plans for available firefighting vehicles in the central data processing system taking into consideration data relating to the terrain and data on available firefighting equipment; transferring the deployment plans generated in the central data processing system to on-board management systems of deployed vehicles; representing deployment data and coordinates corresponding to the deployment plans with output apparatus by the on-board management systems of the

Abstract: The invention relates to a process for the evaluating a received signal of an SAR/MTI pulsed radar system that transmits SAR and MTI pulses with respective definable pulse repetition frequency PRF_SAR and PRF_MTI, such that the received signal is a superimposition consisting of echo pulse sequences of SAR and MTI echo pulse signals. According to the invention, in the received echo pulse sequence of the received signal, each SAR echo from an area of interest is evaluated SAR process. The remaining pulses of the received echo pulse sequence of the received signal are evaluated in using an MTI process.

Abstract: A method and apparatus for planning vehicle trajectories or routing in which a first optimized route between a starting point and a destination is established with regard to a first, relatively coarse node grid, using known techniques. In order to further refine route selection, a second relatively finer node grid is then established within a predeterminable area or volume that is adjacent yo the first optimized route, along its length. The latter finer node grid is then used to establish a second enhanced polygonal path from among the possible polygonal paths between the starting and destination points according to the finer node grid, once again using a known optimization technique.

Abstract: In a method of measuring stress/strain by detecting Barkhausen noise, an exciting/sensing device is arranged at least adjacent to a magnetic or magnetizable element, and passing an increasing magnetizing current through the exciting device. The start of the Barkhausen noise in the element, as a function of the magnetizing current is detected by the sensing device, and the magnetizing current at that time represents a measurement of the stress/strain condition of the element.

Abstract: A force-controlled throttle for adjusting the engine thrust of a combat aircraft with a handle for operation by a pilot and with a signal generating device that is connected to the handle for generating a control signal used for adjusting the engine thrust. The signal generating device is provided for generating the control signal as a function of the force exerted by the pilot on the handle in operation. The throttle may include force-controlled elements for control of an afterburner.

Abstract: A sound pressure level calibrator, which is suitable for sound pressures to be measured in excess of 124 dB and which can be adapted to the installed sound pressure level sensor. This object is attained by a sound pressure level calibrator comprising a pistonphone and a high-pressure adapter connected to the output of the pistonphone. The high-pressure adapter acts as a resonator. With an expanded adapter opening the high-pressure adapter is connected in soundproof manner with the sound pressure level sensor, which is inserted into a structure. The invention can be used for a sound pressure level calibrator to calibrate a sound pressure level sensor, which is integrated into a structure.

Abstract: Lift flap mechanism for adjusting a lift flap assigned to an airplane wing by means of a driving system, the lift flap mechanism comprising a main connection mechanism and a secondary connection mechanism in the form of a guide lever disposed in an articulated manner on the lift flap and the flap track, the main connection mechanism having a steering lever arrangement with at least one steering lever which has a first steering lever joint and a second steering lever joint, the at least one steering lever by way of a pendulum coupled to the first steering lever joint being connected with the flap track, and the second steering lever joint being guided such that, by means of a defined angular position of the at least one steering lever, the positions of the main connection joint and of the secondary connection joint are unambiguously determined.

Abstract: A container, especially intended for use as a workroom, with an adjustable volume includes a base container with a floor panel and a roof panel, and at least one box-shaped expansion element that can be extended from the base container. The expansion element includes a floor panel, a roof panel, a side that is open to the base container, a front panel that is opposite the open side, and two side panels. The container further includes a device with which a box-shaped expansion element can be lowered, such that, once the expansion element has been extended, the floor panels of the expansion element and the base container are at the same height, and with which an expansion element can be raised such that, once the expansion element has been lowered, it can be reinserted into the base container. The roof panel of the box-shaped expansion element is designed to fold along a horizontal axis on the upper edge of the front panel of the expansion element.

Abstract: Cast aluminium alloys comprising 1.0-8.0% in weight magnesium (Mg), >1.0-4.0% in weight silicon (Si), 0.01-<0.5% in weight scandium (Sc), 0.005-0.2% in weight titanium (Ti), 0-0.5% in weight of at least one element or selected from the group consisting of zirconium (Zr), hafnium (Hf), molybdenum (Mo), terbium (Tb), niobium (Nb), gadolinium (Gd), erbium (Er) and vanadium (V), 0-0.8% in weight manganese (Mn), 0-0.3% in weight chromium (Cr), 0-1.0% in weight copper (Cu), 0-0.1% in weight zinc (Zn), 0-0.6% in weight iron (Fe), 0-0.004% in weight beryllium (Be), and the remainder of aluminium with further impurities to an individual maximum of 0.1% in weight and totally maximally 0.5% in weight.

Abstract: A flight sensor for controlling electronic components in an aircraft includes a vibration sensor for converting structure-borne sound to electric vibration signals. A filtering device receives the vibration signals and determines the fraction thereof which is attributable to the aircraft engine, relative to the overall sound in the vibration signals. A comparator compares the engine sound with the overall sound and generates a flight condition signal is based on the result of the comparison, which flight condition signal indicates a defined flight status of the aircraft, such as “flight” or “no flight”. Electronic components on board an aircraft are controlled such that the emission of interfering electromagnetic waves is prevented when the flight status signal indicates that the aircraft is in flight.

Abstract: A camouflage device for camouflaging specularly reflecting surfaces of an object is formed with function elements for influencing the reflection of radiation from an assumed radiation source. Each function element forms a part of an outer layer and has a pair of individual surfaces on its side facing the radiation source. The individual surfaces extend longitudinally side-by-side, and their surfaces are arranged at an angle to one another. The camouflaging device is arrangeable on the object by means of a mechanism such that it is disposed in front of the reflecting surface; and the angular arrangement of the respectively assigned individual surfaces extends such that the surface normal of a first individual surface is sloped downward, and the surface normal of a second individual surface points more steeply than 80° to the horizontal plane, and their surface courses form an angle of <90° with respect to one another.

Abstract: A device for active noise reduction has a chamber, which is arranged laterally in relation to a gas flow, and a chamber opening constructed in one wall of the chamber. In the area of the chamber opening, a deflection device is adjustably arranged. The deflection device, in a first position, at least partially directs the gas flow running by the chamber opening into the chamber, in order to compress air there, and, in a second position, directs the gas from the chamber to the gas flow, in order to release the gas inside the chamber. The resulting alternating pressure inside the chamber is radiated through the chamber opening as sound and overlays the disturbing sound.

Abstract: A high-frequency MEMS switch comprises a signal conductor which is arranged on a substrate and an oblong switching element which has a bent elastic bending area and is fastened on the substrate in a cantilevered manner. An electrode arrangement generates an electrostatic force which bends the switching element toward the signal conductor. The switching element is arranged longitudinally parallel to the signal conductor, and has a contact area which extends transversely to the switch element over the signal conductor. Under the effect of the electrostatic force, the elastic bending area of the switching element progressively approaches the electrode arrangement in a direction parallel to the signal line. The switching element has, for example, two mutually parallel extending switching arms, which are mutually connected by a bridge as the contact area and are arranged on both sides of the signal line and parallel thereto.

Abstract: A camouflage device for camouflaging specularly reflecting surfaces of an object is formed with function elements for influencing the reflection of radiation from an assumed radiation source. Each function element forms a part of an outer layer and has a pair of individual surfaces on its side facing the radiation source. The individual surfaces extend longitudinally side-by-side, and their surfaces are arranged at an angle to one another. The camouflaging device is arrangeable on the object by means of a mechanism such that it is disposed in front of the reflecting surface; and the angular arrangement of the respectively assigned individual surfaces extends such that the surface normal of a first individual surface is sloped downward, and the surface normal of a second individual surface points more steeply than 80° to the horizontal plane, and their surface courses form an angle of <90° with respect to one another.